IT1248285B - Sistema integrato di prelievo da strato limite per avviatore di motore di aereo - Google Patents
Sistema integrato di prelievo da strato limite per avviatore di motore di aereoInfo
- Publication number
- IT1248285B IT1248285B ITMI910585A ITMI910585A IT1248285B IT 1248285 B IT1248285 B IT 1248285B IT MI910585 A ITMI910585 A IT MI910585A IT MI910585 A ITMI910585 A IT MI910585A IT 1248285 B IT1248285 B IT 1248285B
- Authority
- IT
- Italy
- Prior art keywords
- air
- gas turbine
- auxiliary compressor
- turbine engine
- aircraft
- Prior art date
Links
- 239000007858 starting material Substances 0.000 title 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
- F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/50—Application for auxiliary power units (APU's)
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
- Supercharger (AREA)
Abstract
Un turbomotore a gas da aereo è munito di un sistema di rifornimento di aria compressa generalmente usata per soddisfare esigenze specifiche o di aria di prelievo di aereo. Questo sistema di rifornimento di aria compressa comprende un compressore ausiliario, un mezzo per azionare meccanicamente il sistema da un rotore della turbina a gas e un mezzo variatore di ciclo, come un azionatore a velocità variabile, per azionare il ciclo del compressore ausiliario indipendentemente dal ciclo del compressore del turbomotore a gas di aereo. La realizzazione preferita fornisce un mezzo per prelevare aria dallo strato limite fuori dalla navicella o da un'altra parte del guscio esterno di aereo e per usarla come sorgente di aria per il compressore ausiliario. Una realizzazione contiene una turbina ad aria su un albero comune con il compressore ausiliario e un mezzo per dirigere una porzione non usata della corrente di aria dal compressore ausiliario alla turbina ausiliaria allo scopo di aiutare ad azionare il compressore ausiliario e un'altra realizzazione contiene un mezzo per dirigere aria compressa di avviamento alla turbina ad aria per un avviamento a terra e in volo del turbomotore a gas attraverso l'azionatore a velocità variabile e un collegamento meccanico al rotore del turbomotore a gas.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US07/489,150 US5136837A (en) | 1990-03-06 | 1990-03-06 | Aircraft engine starter integrated boundary bleed system |
Publications (3)
Publication Number | Publication Date |
---|---|
ITMI910585A0 ITMI910585A0 (it) | 1991-03-06 |
ITMI910585A1 ITMI910585A1 (it) | 1992-09-06 |
IT1248285B true IT1248285B (it) | 1995-01-05 |
Family
ID=23942622
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
ITMI910585A IT1248285B (it) | 1990-03-06 | 1991-03-06 | Sistema integrato di prelievo da strato limite per avviatore di motore di aereo |
Country Status (7)
Country | Link |
---|---|
US (1) | US5136837A (it) |
JP (1) | JPH04219422A (it) |
CA (1) | CA2036822A1 (it) |
DE (1) | DE4106752A1 (it) |
FR (1) | FR2659389A1 (it) |
GB (1) | GB2242235A (it) |
IT (1) | IT1248285B (it) |
Families Citing this family (74)
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DE4213023A1 (de) * | 1992-04-21 | 1993-10-28 | Asea Brown Boveri | Verfahren zum Betrieb eines Gasturbogruppe |
GB9415436D0 (en) * | 1994-07-30 | 1994-09-21 | Provost Michael J | Auxiliary gas turbine engines |
US5779196A (en) * | 1995-12-08 | 1998-07-14 | The Boeing Company | Ram air drive laminar flow control system |
US5721402A (en) * | 1996-09-09 | 1998-02-24 | Northrop Grumman Corporation | Noise suppression system for a jet engine |
US5923003A (en) * | 1996-09-09 | 1999-07-13 | Northrop Grumman Corporation | Extended reaction acoustic liner for jet engines and the like |
US6735953B1 (en) * | 1997-12-22 | 2004-05-18 | Allied Signal Inc. | Turbomachine-driven environmental control system |
US6305156B1 (en) | 1999-09-03 | 2001-10-23 | Alliedsignal Inc. | Integrated bleed air and engine starting system |
CA2329555A1 (en) * | 2000-12-22 | 2002-06-22 | Jose Albero | Main propulsion engine system integrated with secondary power unit |
US6968701B2 (en) | 2002-01-16 | 2005-11-29 | United Technologies Corporation | Engine integrated auxiliary power unit |
US6920748B2 (en) * | 2002-07-03 | 2005-07-26 | General Electric Company | Methods and apparatus for operating gas turbine engines |
US6655632B1 (en) | 2002-08-27 | 2003-12-02 | General Electric Company | System and method for actively changing an effective flow-through area of an inlet region of an aircraft engine |
US6990797B2 (en) * | 2003-09-05 | 2006-01-31 | General Electric Company | Methods and apparatus for operating gas turbine engines |
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US7353647B2 (en) * | 2004-05-13 | 2008-04-08 | General Electric Company | Methods and apparatus for assembling gas turbine engines |
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FR2875855B1 (fr) * | 2004-09-27 | 2006-12-22 | Snecma Moteurs Sa | Turboreacteur avec un bras monobloc de raccord de servitudes et le bras monobloc de raccord de servitudes |
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FR2911915B1 (fr) * | 2007-01-30 | 2011-06-17 | Hispano Suiza Sa | Dispositif de refroidissement d'un equipement electrique dans une turbomachine. |
US7766280B2 (en) * | 2007-05-29 | 2010-08-03 | United Technologies Corporation | Integral suction device with acoustic panel |
US9157368B2 (en) * | 2007-09-05 | 2015-10-13 | United Technologies Corporation | Active flow control for nacelle inlet |
US20100236637A1 (en) * | 2007-10-05 | 2010-09-23 | Hendrix Jr James Edward | Surface Ventilator For A Compliant-Surface Flow-Control Device |
US9719428B2 (en) * | 2007-11-30 | 2017-08-01 | United Technologies Corporation | Gas turbine engine with pylon mounted accessory drive |
US20100162680A1 (en) * | 2008-12-31 | 2010-07-01 | Syed Jalaluddin Khalid | Gas turbine engine with ejector |
US8572947B2 (en) * | 2008-12-31 | 2013-11-05 | Rolls-Royce Corporation | Gas turbine engine with ejector |
JP5246425B2 (ja) * | 2009-05-19 | 2013-07-24 | 株式会社Ihi | 航空機用ジェットエンジンの騒音低減装置と方法 |
US20100326085A1 (en) * | 2009-06-25 | 2010-12-30 | Veilleux Leo J | Lightweight start system for a gas turbine engine |
US8267122B2 (en) | 2009-06-30 | 2012-09-18 | Ge Aviation Systems Llc | Method and systems for bleed air supply |
DE102009033755A1 (de) * | 2009-07-17 | 2011-01-20 | Rolls-Royce Deutschland Ltd & Co Kg | Turbofantriebwerk |
CA2806567C (en) | 2010-07-26 | 2019-06-18 | Rolls-Royce Corporation | Gas turbine engine with ejector |
US8974177B2 (en) * | 2010-09-28 | 2015-03-10 | United Technologies Corporation | Nacelle with porous surfaces |
EP2622192A2 (en) * | 2010-09-30 | 2013-08-07 | General Electric Company | Aircraft engine systems and methods for operating same |
US8978351B2 (en) | 2011-10-21 | 2015-03-17 | United Technologies Corporation | Integrated thermal management system and environmental control system for a gas turbine engine |
US10125724B2 (en) | 2012-01-17 | 2018-11-13 | United Technologies Corporation | Start system for gas turbine engines |
DE102012218135B4 (de) * | 2012-10-04 | 2017-07-27 | Rolls-Royce Deutschland Ltd & Co Kg | Lagerkammerentlüftungssystem für ein Flugzeugtriebwerk und Verfahren zum Bereitstellen eines gewünschten Druckverhältnisses an Lagerkammerdichtungen einer luftgedichteten Lagerkammer |
US9630706B2 (en) | 2013-02-22 | 2017-04-25 | Rolls-Royce Corporation | Positionable ejector member for ejector enhanced boundary layer alleviation |
US9810158B2 (en) * | 2014-04-01 | 2017-11-07 | The Boeing Company | Bleed air systems for use with aircraft and related methods |
US10054051B2 (en) * | 2014-04-01 | 2018-08-21 | The Boeing Company | Bleed air systems for use with aircraft and related methods |
FR3020410B1 (fr) * | 2014-04-29 | 2021-09-17 | Snecma | Turbomachine d'aeronef a prelevement de puissance mecanique ameliore |
EP3164576B1 (en) | 2014-07-03 | 2020-07-29 | General Electric Company | Jet engine cold air cooling system and corresponding method |
FR3024180B1 (fr) * | 2014-07-28 | 2016-07-22 | Turbomeca | Dispositif pneumatique de reactivation rapide d'un turbomoteur, architecture d'un systeme propulsif d'un helicoptere multi-moteur equipe d'un tel dispositif et helicoptere correspondant |
GB201416928D0 (en) * | 2014-09-25 | 2014-11-12 | Rolls Royce Plc | A gas turbine and a method of washing a gas turbine engine |
FR3026435B1 (fr) * | 2014-09-29 | 2016-10-21 | Turbomeca | Dispositif et procede de test d'integrite d'un systeme de reactivation rapide d'un turbomoteur d'un helicoptere |
GB201506396D0 (en) | 2014-12-11 | 2015-05-27 | Rolls Royce Plc | Cabin blower system |
GB201508545D0 (en) | 2015-05-19 | 2015-07-01 | Rolls Royce Plc | Compressor tip injector |
US10100744B2 (en) | 2015-06-19 | 2018-10-16 | The Boeing Company | Aircraft bleed air and engine starter systems and related methods |
US20170081020A1 (en) * | 2015-09-22 | 2017-03-23 | Rohr, Inc. | Active laminar flow control system with drainage |
GB201600180D0 (en) * | 2016-01-06 | 2016-02-17 | Rolls Royce Plc | Gas turbine engine |
GB201602710D0 (en) | 2016-02-16 | 2016-03-30 | Rolls Royce | Cabin blower system |
US20170306847A1 (en) * | 2016-04-26 | 2017-10-26 | United Technologies Corporation | Combined Drive for Cooling Air Using Cooing Compressor and Aircraft Air Supply Pump |
US10457401B2 (en) * | 2016-05-13 | 2019-10-29 | United Technologies Corporation | Dual-use air turbine system for a gas turbine engine |
US10870490B2 (en) | 2016-05-26 | 2020-12-22 | Hamilton Sunstrand Corporation | Energy flow |
US11511867B2 (en) | 2016-05-26 | 2022-11-29 | Hamilton Sundstrand Corporation | Mixing ram and bleed air in a dual entry turbine system |
US11506121B2 (en) * | 2016-05-26 | 2022-11-22 | Hamilton Sundstrand Corporation | Multiple nozzle configurations for a turbine of an environmental control system |
US10443622B2 (en) * | 2016-06-13 | 2019-10-15 | United Technologies Corporation | Active core cooling system |
GB201611104D0 (en) * | 2016-06-27 | 2016-08-10 | Rolls Royce Plc | Tip clearance control system |
US11203949B2 (en) * | 2016-08-11 | 2021-12-21 | General Electric Company | Mechanically driven air vehicle thermal management device |
US11105265B2 (en) * | 2016-09-02 | 2021-08-31 | Raytheon Technologies Corporation | Supplemental cooling air for turbine exhaust components and surfaces |
US10767564B2 (en) | 2017-03-17 | 2020-09-08 | Hamilton Sunstrand Corporation | Air turbine starter with automated variable inlet vanes |
US10443506B2 (en) * | 2017-07-26 | 2019-10-15 | Unison Industries, Llc | Air turbine starter |
US10823014B2 (en) * | 2017-12-13 | 2020-11-03 | General Electric Company | Turbine engine for reducing rotor bow and method thereof |
US10634057B2 (en) | 2018-01-19 | 2020-04-28 | Hamilton Sundstrand Corporation | Airflow control for air turbine starter |
US11073091B2 (en) * | 2018-06-14 | 2021-07-27 | General Electric Company | Gas turbine engine with integrated air cycle machine |
US10954865B2 (en) | 2018-06-19 | 2021-03-23 | The Boeing Company | Pressurized air systems for aircraft and related methods |
US11433990B2 (en) | 2018-07-09 | 2022-09-06 | Rohr, Inc. | Active laminar flow control system with composite panel |
US11041444B2 (en) | 2018-11-02 | 2021-06-22 | Pratt & Whitney Canada Corp. | Gas turbine engine with differential gearbox |
US11465757B2 (en) | 2018-12-06 | 2022-10-11 | The Boeing Company | Systems and methods to produce aircraft cabin supply air |
US11035251B2 (en) | 2019-09-26 | 2021-06-15 | General Electric Company | Stator temperature control system for a gas turbine engine |
FR3109966B1 (fr) * | 2020-05-07 | 2022-09-09 | Safran Helicopter Engines | Procédé de commande et unité de commande pour éviter le pompage d’un compresseur de charge dans un groupe auxiliaire de puissance |
CN112211725B (zh) * | 2020-09-11 | 2023-03-24 | 中国航空工业集团公司成都飞机设计研究所 | 一种适用于无人机的辅助能源控制***及控制方法 |
FR3116082B1 (fr) * | 2020-11-09 | 2022-09-30 | Safran Aircraft Engines | Turboréacteur à double flux pourvu de moyens de communication d’air |
GB202118069D0 (en) | 2021-12-14 | 2022-01-26 | Rolls Royce Plc | Blower assembly |
US11788465B2 (en) * | 2022-01-19 | 2023-10-17 | General Electric Company | Bleed flow assembly for a gas turbine engine |
CN114771804B (zh) * | 2022-06-17 | 2022-09-02 | 中国空气动力研究与发展中心低速空气动力研究所 | 非对称凹槽液膜定向飞溅气动结构 |
GB2624170A (en) * | 2022-11-08 | 2024-05-15 | Rolls Royce Plc | Rotary assembly |
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DE3272914D1 (en) * | 1981-10-06 | 1986-10-02 | Kongsberg Vapenfab As | Turbo-machines with bleed-off means |
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US4708030A (en) * | 1985-03-18 | 1987-11-24 | Sundstrand Corporation | Multi-range starter-generator drive |
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US4749150A (en) * | 1985-12-24 | 1988-06-07 | Rohr Industries, Inc. | Turbofan duct with noise suppression and boundary layer control |
US4684081A (en) * | 1986-06-11 | 1987-08-04 | Lockheed Corporation | Multifunction power system for an aircraft |
US4743776A (en) * | 1986-09-02 | 1988-05-10 | Sundstrand Corporation | Starter-generator for engines |
FR2609686B1 (fr) * | 1987-01-16 | 1992-03-13 | Abg Semca | Installation de conditionnement d'air a haut rendement pour engin aeronautique |
JPS6469721A (en) * | 1987-09-02 | 1989-03-15 | Sundstrand Corp | Multipurpose auxiliary power device |
US4777376A (en) * | 1987-12-18 | 1988-10-11 | Sundstrand Corporation | Lightweight starting system for an electrically compensated constant speed drive |
-
1990
- 1990-03-06 US US07/489,150 patent/US5136837A/en not_active Expired - Fee Related
-
1991
- 1991-02-21 CA CA002036822A patent/CA2036822A1/en not_active Abandoned
- 1991-03-01 GB GB9104388A patent/GB2242235A/en not_active Withdrawn
- 1991-03-01 FR FR9102447A patent/FR2659389A1/fr active Pending
- 1991-03-02 DE DE4106752A patent/DE4106752A1/de not_active Ceased
- 1991-03-04 JP JP3060967A patent/JPH04219422A/ja active Pending
- 1991-03-06 IT ITMI910585A patent/IT1248285B/it active IP Right Grant
Also Published As
Publication number | Publication date |
---|---|
CA2036822A1 (en) | 1991-09-07 |
FR2659389A1 (fr) | 1991-09-13 |
ITMI910585A1 (it) | 1992-09-06 |
GB9104388D0 (en) | 1991-04-17 |
JPH04219422A (ja) | 1992-08-10 |
GB2242235A (en) | 1991-09-25 |
US5136837A (en) | 1992-08-11 |
DE4106752A1 (de) | 1991-09-12 |
ITMI910585A0 (it) | 1991-03-06 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
0001 | Granted |